Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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analyzer. and SHARPO, a general-purpose CFD code developed at Thiokol Propulsion. SHARP was modified so that friction, heat transfer, mass addition, as well as minor losses in one-dimensional flow can be taken into account. The pressure, temperature and velocity of the combustion gas in the leak paths are calculated in SHARP by solving the time-dependent Navier-Stokes equations while the heat conduction in the solid is modeled by SINDA/G. The two codes are coupled by the heat flux at the solid-gas interface. A few test cases are presented and the results from SFLOW agree very well with the exact solutions or experimental data. These cases include Fanno flow where friction is important, Rayleigh flow where heat transfer between gas and solid is important, flow with mass addition due to the erosion of the solid wall, a transient volume venting process, as well as some transient one-dimensional flows with analytical solutions. In addition, SFLOW is applied to model the RSRM nozzle joint 4 subscale hotflow tests and the predicted pressures, temperatures (both gas and solid), and O-ring erosions agree well with the experimental data. It was also found that the heat transfer between gas and solid has a major effect on the pressures and temperatures of the fill bottles in the RSRM nozzle joint 4 configuration No. 8 test. Derived from text Computational Fluid Dynamics; Gas Dynamics; Heat Transfer; Applications Programs (Computers); Joints (Junctions); Navier- Stokes Equation; Space Shuttle Boosters; Thermal Analysis 20000066593 Prins Maurits Lab. TNO, Rijswijk, Netherlands Analysis of the Lifetime Critical Components of the Hellfire 2 Missile and the Hydra 70, 2.75” Rocket Final Report Een Analyse van de Levensduurkritische Elementen van het Hellfire II Missile en de 2.75” Hydra 70 Raket Keizers, H. L. J., Prins Maurits Lab. TNO, Netherlands; Thomassen, H. J. M., Prins Maurits Lab. TNO, Netherlands; Klein, A. A. J., Prins Maurits Lab. TNO, Netherlands; August 1999; 26p; In Dutch; Original contains color illustrations Contract(s)/Grant(s): A98/KLu/445; TNO Proj. 014.11175 Report No.(s): TD99-0115; PML-1999-A20; Copyright; Avail: Issuing Activity In 1998, a system level study is performed into the lifetime critical aspects of the Hellfire 2 missile and the Hydra 70, 2.75” rocket. The purpose of this study was to identify the lifetime critical components of both systems, in order to assist the Royal Netherlands Airforce on both systems in the coming years. For the Hellfire system this will consist of technical support in field surveillance programme, which is probably going to be performed at AMCOM (USA). For the Hydra 70, test activities and technical support are foreseen. For both systems it is anticipated that the energetic components will become lifetime limiting. If stored under well controlled conditions, a lifetime larger than 10 years seems possible for both systems. The effect of operational conditions in terms of number of captive flight hours, temperature and humidity levels is unknown. It is recommended to obtain information on these effects. Together with information on the ageing characteristics of the systems, this information can probably be used to extent the lifetime or to increase the safety of both systems. Author Surveillance; Captive Tests; Air to Surface Missiles; Air to Air Missiles 20000067640 NASA Marshall Space Flight Center, Huntsville, AL USA Propulsion Options For Interstellar Exploration Johnson, Les, NASA Marshall Space Flight Center, USA; Leifer, Stephanie, Jet Propulsion Lab., California Inst. of Tech., USA; [2000]; 1p; In English; 36th; 36th Joint Propulsion Conference, 17-19 Jul. 2000, Huntsville, AL, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA; No Copyright; Avail: Issuing Activity; Abstract Only NASA is considering missions to explore near-interstellar space (40 - 250 Astronomical Units) early in the next decade as the first step toward a vigorous interstellar exploration program. A key enabling technology for such an ambitious science and exploration effort is a propulsion system capable of providing fast trip times, yet which has low enough mass to allow for the use of inexpensive launch vehicles. Advanced propulsion technologies that might support the First interstellar precursor mission by the end of the first decade of the new millennium include solar sails and nuclear electric propulsion. Solar sails and electric propulsion are two technology areas that may hold promise for the next generation of interstellar precursor missions as well - perhaps a thousand astronomical units traveled in a professional lifetime. Future missions to far beyond the Heliosphere will require the development of propulsion technologies that are only at the conceptual stage today. For years, the scientific community has been interested in solar sail and electric propulsion technologies to support robotic exploration of the solar system. Progress in thin-film materials fabrication and handling, and advancement in technologies that may enable the deployment of large sails in space are only now maturing to the point where ambitious interstellar precursor missions using sails can be considered. Xenon ion propulsion is now being demonstrated for planetary exploration by the Deep Space 1 mission. The primary issues for the adaptation of electric propulsion to interstellar precursor applications include the development of low specific mass nuclear power systems, 40
engine lifetime, and high power operation. Recent studies of interstellar precursor mission scenarios that use these propulsion systems will be described, and the range of application of each technology will be explored. Author Interstellar Space; Space Exploration; Propulsion System Configurations; Propulsion System Performance 20000067658 NASA Marshall Space Flight Center, Huntsville, AL USA A Design Tool for Liquid Rocket Engine Injectors Farmer, R., SECA, Inc., USA; Cheng, G., SECA, Inc., USA; Trinh, H., NASA Marshall Space Flight Center, USA; Tucker, K., NASA Marshall Space Flight Center, USA; [2000]; 12p; In English; Joint Propulsion, 17-19 Jul. 2000, Huntsville, AL, USA; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche A practical design tool which emphasizes the analysis of flowfields near the injector face of liquid rocket engines has been developed and used to simulate preliminary configurations of NASA’s Fastrac and vortex engines. This computational design tool is sufficiently detailed to predict the interactive effects of injector element impingement angles and points and the momenta of the individual orifice flows and the combusting flow which results. In order to simulate a significant number of individual orifices, a homogeneous computational fluid dynamics model was developed. to describe sub- and supercritical liquid and vapor flows, the model utilized thermal and caloric equations of state which were valid over a wide range of pressures and temperatures. The model was constructed such that the local quality of the flow was determined directly. Since both the Fastrac and vortex engines utilize RP-1/LOX propellants, a simplified hydrocarbon combustion model was devised in order to accomplish three-dimensional, multiphase flow simulations. Such a model does not identify drops or their distribution, but it does allow the recirculating flow along the injector face and into the acoustic cavity and the film coolant flow to be accurately predicted. Author Combustible Flow; Computational Fluid Dynamics; Injectors; Liquid Propellant Rocket Engines; Three Dimensional Flow; Navier-Stokes Equation; Vorticity 23 CHEMISTRY AND MATERIALS (GENERAL) �� 20000063529 Universal Energy Systems, Inc., Dayton, OH USA Advanced Thermal Barrier Coating Final Report, 3 May 1999 - 3 Feb 2000 Bhattacharya, Rabi S.; Apr. 26, 2000; 29p; In English Contract(s)/Grant(s): F33615-99-C-5206 Report No.(s): AD-A377045; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche The primary research objective of this work was to develop a novel thermal barrier coating (TBC) system by depositing a high quality alpha alumina sublayer on the metallic bond-coat, prior to the deposition of the yttria stabilized zirconia (YSZ) coating. We have used a patented filtered cathodic arc deposition equipment to deposit an alpha alumina layer on a superalloy that was plasma-spray coated with a NiCoCrAlY bond-coat. The filtered arc coating process allows droplet-free deposition of coatings. Also, this process provides high ionization (> 90%) compared with the standard physical vapor deposition processes (is less than 20%), thereby providing excellent bonding between the coating and the substrate. Using this approach, 0.5 - 0.6 micron thick alpha alumina coatings were deposited on metallic substrate at 925 deg C. Oxidation tests reveal that further improvements are necessary for the system to perform better than state-of-the-art TBCs. The performance was impaired by microstructural instability and surface rumpling of the bond-coat, which caused failure of the alumina layer at a number of locations. DTIC Thermal Control Coatings; Yttria-Stabilized Zirconia; Yttrium Oxides; Heat Resistant Alloys; Turbines 20000064083 California Univ., Dept. of Pharmaceutical Chemistry, San Francisco, CA USA Interaction of a Model Peptide with a Water--Bilayer System Pohorille, A., California Univ., USA; Wilson, M. A., California Univ., USA; Structure and Reactivity in Aqueous Solution: Characterization of Chemical and Biological Systems; 1994; ISSN 0097-6156, pp. 395-408; In English Contract(s)/Grant(s): NCC2-772; NCA2-792; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche 41
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Scientific and Technical Aerospace
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Introduction Scientific and Technic
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Subject Divisions Table of Contents
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ground equipment and systems. For a
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Subject Categories of the Division
Page 11 and 12: 48 Oceanography 139 Includes the ph
Page 13 and 14: 72 Atomic and Molecular Physics 191
Page 15 and 16: Document Availability Information T
Page 17 and 18: Avail: NASA Public Document Rooms.
Page 19 and 20: NASA CASI Price Tables — Effectiv
Page 21 and 22: ALABAMA AUBURN UNIV. AT MONTGOMERY
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Page 25 and 26: 20000061433 Pisa Univ., Dipartiment
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Page 29 and 30: ciency of the generated derivative
Page 31 and 32: 20000063509 NASA Glenn Research Cen
Page 33 and 34: 05 AIRCRAFT DESIGN, TESTING AND PER
Page 35 and 36: A long tradition of aerodynamic des
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Page 43 and 44: performance required for a proposed
Page 45 and 46: ment cost and create better product
Page 47 and 48: tion (NPSS), is focused on the inte
Page 49 and 50: surface measurement techniques used
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Page 55 and 56: primary issues for it’s adaptatio
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Page 61: necessary for ignition modeling, or
Page 65 and 66: 24 COMPOSITE MATERIALS ��
Page 67 and 68: ments. For the screening of liner m
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Page 71 and 72: 20000065655 Ames Lab., IA USA Funda
Page 73 and 74: This is a second Triennial Conferen
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Page 79 and 80: Spacecraft in low Earth orbit (LEO)
Page 81 and 82: Pressure gradients, i.e. pressure h
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Page 87 and 88: 20000064078 Physics and Electronics
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Page 101 and 102: other, The theoretical framework go
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37 MECHANICAL ENGINEERING ��
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solver based on overset grid techno
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20000067659 NASA Marshall Space Fli
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20000064621 Rensselaer Polytechnic
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that for a specific example of a be
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km x 1000 km). As with the nearly c
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20000064527 Analytical Imaging and
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20000064533 Austin State Univ., Dep
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20000064539 California Univ., Inst.
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20000064547 Jet Propulsion Lab., Ca
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in Yellowstone National Park. We ar
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terns of community hysteresis based
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20000064565 Jet Propulsion Lab., Ca
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tion model (DEM) fitting to the sca
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The Carolina slate belt is a 10- to
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20000063373 Los Alamos National Lab
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20000064912 New Energy and Industri
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and discusses the issues and resear
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The objective of this study was to
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distributions with engine test resu
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7.6, while the 1926 events appear t
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We investigate the compositional di
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Flight Center, USA; Moore, T. E., N
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This report presents the Applied Me
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in Goa, India, by 3 - 4 days. Wind
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51 LIFE SCIENCES (GENERAL) Includes
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20000062717 Joint Inst. for Nuclear
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20000064015 Institute for Human Fac
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during 50% (SD 4%) of the breathing
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20000064711 Massachusetts Inst. of
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The analysis of this smaller data s
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vided a functional helmet mount. Th
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61 COMPUTER PROGRAMMING AND SOFTWAR
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The goal of multi-image classificat
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20000063526 Defence Science and Tec
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85 dB amplifier design evolved by o
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20000064594 New Mexico Univ., Elect
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20000064615 NASA Ames Research Cent
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declarations with a pattern recogni
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containing point where interpolatio
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has his own responsibility, while t
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the people, documents and projects
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and experimental technology, many o
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tems. In particular this applicatio
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Over the past decade, high performa
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expensive than a single analysis. I
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20000064726 Carnegie-Mellon Univ.,
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20000064099 Teledyne Brown Engineer
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20000066597 Geophysical Observatory
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20000065633 Institute TNO of Applie
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important conclusion is that for su
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est frame of the string. The modifi
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isotopes. The method and program we
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A detailed study is undertaken, usi
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20000063497 Kaiser Electro-Optics,
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delivers 60% of the x-ray flux from
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76 SOLID-STATE PHYSICS ��
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20000064660 Abdus Salam Internation
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20000067648 NASA Marshall Space Fli
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20000064703 Institute of Atomic Ene
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The BRST approach is applied to the
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20000067671 Hampton Univ., VA USA A
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82 DOCUMENTATION AND INFORMATION SC
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ecoming almost too cumbersome to be
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physical world. These are the two p
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with WFPC2 data. Tests of HSTphot
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A brief description is given of the
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20000064070 NASA Ames Research Cent
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gas, show variations that have rema
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egy, called Power In that would all
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20000065631 NASA Kennedy Space Cent
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20000064089 Smithsonian Astrophysic
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A ABERRATION, 143, 198 ABRASION, 22
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COMPRESSIBLE FLOW, 83 COMPRESSION L
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FATIGUE (MATERIALS), 50, 93, 96 FAT
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LASING, 90 LATE STARS, 224 LATITUDE
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PATCH ANTENNAS, 74 PATHOLOGY, 98 PA
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SPACE PLATFORMS, 38 SPACE PROBES, 2
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WIND PROFILES, 137 WIND TUNNEL TEST
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Brown, Andy, 38 Brown, April S., 20
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Grosvenor, C. A., 70 Grosvenor, J.
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Lu, Gui-Ying, 50 Lugg, Desmond J.,
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Robertson, Tony, 39 Robinson, Jeffr
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Warner, J. D., 63 Warren, James, 16
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Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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